EP0217686A1 - Flugzeug des Fallschirmflügeltyps - Google Patents

Flugzeug des Fallschirmflügeltyps Download PDF

Info

Publication number
EP0217686A1
EP0217686A1 EP86401692A EP86401692A EP0217686A1 EP 0217686 A1 EP0217686 A1 EP 0217686A1 EP 86401692 A EP86401692 A EP 86401692A EP 86401692 A EP86401692 A EP 86401692A EP 0217686 A1 EP0217686 A1 EP 0217686A1
Authority
EP
European Patent Office
Prior art keywords
pilot
engine
machine
lines
guide rail
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP86401692A
Other languages
English (en)
French (fr)
Other versions
EP0217686B1 (de
Inventor
Marc Ranjon
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
AERONAUTIQUE SERVICE
Original Assignee
AERONAUTIQUE SERVICE
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by AERONAUTIQUE SERVICE filed Critical AERONAUTIQUE SERVICE
Publication of EP0217686A1 publication Critical patent/EP0217686A1/de
Application granted granted Critical
Publication of EP0217686B1 publication Critical patent/EP0217686B1/de
Expired legal-status Critical Current

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C31/00—Aircraft intended to be sustained without power plant; Powered hang-glider-type aircraft; Microlight-type aircraft
    • B64C31/028—Hang-glider-type aircraft; Microlight-type aircraft
    • B64C31/036—Hang-glider-type aircraft; Microlight-type aircraft having parachute-type wing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C31/00—Aircraft intended to be sustained without power plant; Powered hang-glider-type aircraft; Microlight-type aircraft
    • B64C31/02—Gliders, e.g. sailplanes
    • B64C31/024—Gliders, e.g. sailplanes with auxiliary power plant

Definitions

  • the present invention relates to a flying machine of the type provided with a parachute wing and more particularly to improvements made to such a machine.
  • Flying machines of the aforementioned type are already known and they comprise a tricycle comprising a tubular chassis of welded aluminum and a propeller motor fixed to a trellis.
  • the parachute wing is fixed to the chassis by means of lift lines.
  • Steering control both on the ground and in flight, is done by means of a lifter which is controlled by the pilot's feet and to which are attached right and left steering (or steering) lines for the right turn and left, respectively.
  • the spreader is combined with the front wheel, the two rear wheels being damped to constitute what is called "main landing gear".
  • the object of the present invention is to eliminate the drawbacks of said flying machines, namely to provide a flying machine of the type provided with a parachute wing which better meets the needs of the practice than machines aiming at the same object previously known, in particular in what: . take-off of the craft can also be done during normal taxiing without having to stop the engine to transform the land craft into a flying craft; . the direction of control of the machine is done without risk of false operation, and in particular of unwanted braking and therefore without risk of stalling; . the suspension lines are adjustable to the weight of the pilot which allows perfect balance of the craft giving the pilot a feeling of comfort in flight.
  • the subject of the present invention is a machine of the type comprising in combination: . a tubular chassis on wheels; . an engine fitted with a propeller; . a parachute type wing which is intended to make the flying machine, under the driving action of the engine and the concomitant effect of the wind, this wing being fixed to said chassis by suspension lines, right and left, and being stored in a bag in condition of not using the machine or rolling on the ground thereof; . a pilot seat mounted on said chassis; .
  • a spreader for controlling the direction of the craft on the ground and in flight, actuated by the pilot's feet, which in turn actuates the steering lines, right and left, connected laterally to the parachute wing, said propeller and said pilot seat, and therefore the pilot, being protected by tubular arches forming an integral part of said tubular chassis, which machine is characterized in that the bag containing the parachute wing is equipped with ejection means, known per se , parachute wing allowing the automatic opening of the latter, under the action driving the engine and the concomitant effect of the wind, takes place during normal taxiing without having to stop the engine beforehand, said ejection means being mechanical or pyrotechnic or of another type known per se.
  • the machine according to the invention comprising a front wheel and two rear wheels, can also be equipped: . a first lifting beam consisting of a single bar of steering control actuated by the feet of the pilot and pivoting around a single vertical axis with which said front wheel is conjugated, the two ends of said single bar being connected to the steering lines right and left, respectively; . and / or adjustable fixing means for the right and left lifting lines as a function of the weight of the pilot and therefore of the center of gravity of the machine / pilot assembly.
  • the flying object represented in FIGS. 1 to 3 is of the type comprising a parachute wing 1, which is folded in a bag 19, when it is not used, and which is connected to a chassis 2 with a tubular structure, in particular in welded aluminum, by means of suspension lines 3 a , the steering control being done using a lifting beam 4 connected to control lines 3 b which are attached at the top to the lateral edges of the wing 1 for then conveying downwards together with said suspension lift 3 has in the cables 5 and continue independently of the latter to said lifter.
  • the chassis supports an engine 6 fitted with a propeller 7 and a pilot seat 8, and comprises protection arches for the pilot and the propeller 7, such as 9 a , 9 b , 9 c , 9 d .
  • This propeller is constituted in particular by a four-blade propeller, made of composite materials, whose function is to promote the opening of the parachute wing at the start.
  • a fuel tank 10 with a pump 10 a .
  • the reference numerals 11, 12 and 13 respectively represent the engine starting cable, the handle or throttle for controlling the rise, cruise or descent of the machine, and the exhaust pipe.
  • the chassis also rests on three wheels, including a front wheel 14 and two rear wheels 15 and 16, the latter being damped as is the seat 8 while the front wheel 14 is conjugated, in a manner known per se, with said spreader 4 , so that the actuation of the latter acts not only on said steering lines, but also on the front wheel 14.
  • the lifter 4 is constituted by a single bar 17 for steering control pivoting about a vertical axis 18 of conjugation between the lifter and the front wheel 14, under the action of the driver's feet.
  • the bag 19, containing the wing 1 in the folded state is fitted with ejection means, of a type known per se (and therefore not shown) of this airfoil, which allows the takeoff of the craft when it is rolling on the ground, without having to stop the engine to perform the necessary manual takeoff and display maneuvers on the ground with existing gear.
  • Figure 2 shows the parachute wing 1 in the unfolded state after entry into function of its ejection means, the latter may be constituted by mechanical means, and notably by an opening handle, or by pyrotechnic means .
  • the bag can be positioned at any point a priori on the chassis, but that it is preferably arranged on its rear upper part, as shown in FIGS. 1 and 3, the cables 5 connecting the suspension lines. 3 has one of the wing-folded in the bag to the side tubes 31 of substantially horizontal frame 2, through adjustable fixing means 32 according to the invention.
  • Such adjustable fastening means of said suspension lift has 3 are shown in Figures 4 to 6, and correspond to a preferred embodiment, but not limiting. They comprise a guide rail 20 in T of a slide 21 provided with a base 22 in, namely in the form of ⁇ open on one side, sliding along the transverse and substantially horizontal segment of the T. This base is surmounted by a central handle 23 provided with a ring 25 defining a window 24 through which pass the suspension lift 3a, from said 5 cable which are fastened around the ring 25 and the steering lines 3b, also coming from the cable 5 but moving downward to be attached to said spreader 4.
  • the handle 23 is also provided with another window (or of a housing) 26 which is delimited by a frame or ring 33 adjacent to the ring 25 and intended to house a pin 27 with spring 28 for automatic locking, this axis cooperating with an unlocking disc 29 allowing 'extract the shaft 27 from a blocking hole 30 to introduce it into another similar hole, these holes 30 being formed axially on the transverse and horizontal segment of the guide T.
  • a guide rail 20 is fixed to each of said two substantially horizontal lateral tubes 31 of the chassis 2, in particular by bolting (cf. also the reference numeral 32 in FIG. 1).
  • the spacing between two contiguous holes 30 is calculated appropriately to allow effective adjustment according to the weight of the pilot. It is clear that, if the initial position of the slide 21 (and therefore of the point of attachment of the lift lines) is that of FIG. 4 and if the center of gravity of the machine / pilot assembly is on the left or on the right from this initial position, it suffices to grasp the slide 21 by its handle 23 while lifting the unlocking disc 29 and to move the slide to the left or to the right, respectively, so as to insert the locking pin 27 into that of the holes 30 which is contained substantially in the plane passing through the result of the forces acting on the machine / pilot in flight assembly.
  • This adjustment operation of the point of attachment of the suspension lines of the parachute can be facilitated by graduating the rail 20, that is to say by associating with each hole 30 a weight value of the pilot for which the dynamic balance of the suspended machine / pilot assembly, directly as a function of the weight of the pilot, the variation range of which is known with very good approximation, and by associating with the slide 21 an index or mark (the weight value scale and the index are not shown).

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Motorcycle And Bicycle Frame (AREA)
  • Toys (AREA)
  • Catching Or Destruction (AREA)
EP19860401692 1985-08-02 1986-07-29 Flugzeug des Fallschirmflügeltyps Expired EP0217686B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8511865A FR2585668B1 (fr) 1985-08-02 1985-08-02 Perfectionnements apportes aux engins volants du type a voilure parachute
FR8511865 1985-08-02

Publications (2)

Publication Number Publication Date
EP0217686A1 true EP0217686A1 (de) 1987-04-08
EP0217686B1 EP0217686B1 (de) 1988-10-19

Family

ID=9321920

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19860401692 Expired EP0217686B1 (de) 1985-08-02 1986-07-29 Flugzeug des Fallschirmflügeltyps

Country Status (3)

Country Link
EP (1) EP0217686B1 (de)
DE (1) DE3660954D1 (de)
FR (1) FR2585668B1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108945427A (zh) * 2018-07-24 2018-12-07 深圳市百川融创科技有限公司 用于冲压翼伞的弹射回收装置
CN109823531A (zh) * 2019-03-13 2019-05-31 深圳市百川融创科技有限公司 一种基于冲压翼伞绳的弹射回收装置

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB8703299D0 (en) * 1987-02-13 1987-03-18 Powerchute Systems Internation Light aircraft
FR2645474B1 (fr) * 1989-04-11 1991-06-07 David Jean Pierre Dispositif permettant de transformer une motocyclette en aeronef ultra-leger motorise
US5620153A (en) * 1995-03-20 1997-04-15 Ginsberg; Harold M. Light aircraft with inflatable parachute wing propelled by a ducted propeller
RU2584353C1 (ru) * 2015-02-16 2016-05-20 Юрий Витальевич Швед Конструктивные элементы для повышения безопасности летательных аппаратов с мягким крылом

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2957664A (en) * 1960-10-25 Fast-acting parachutes
GB2098563A (en) * 1981-05-15 1982-11-24 Dell Simon Charles Self-inflating flexible wing
DE3321499A1 (de) * 1983-06-15 1984-01-05 Dieter Dipl.-Ing. Unbehaun (FH), 8500 Nürnberg Eigenstartfaehiges luftfahrzeug mit geringen packmassen
GB2127764A (en) * 1982-09-30 1984-04-18 Jones Andrew Wil Free flyable structure
US4445654A (en) * 1982-06-21 1984-05-01 Handbury James W Aircraft recovery chute
EP0130925A1 (de) * 1983-03-11 1985-01-09 Stephen L. Snyder Motorisierter Hängeleiter mit fallschirmförmigem Tragflügel

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2957664A (en) * 1960-10-25 Fast-acting parachutes
GB2098563A (en) * 1981-05-15 1982-11-24 Dell Simon Charles Self-inflating flexible wing
US4445654A (en) * 1982-06-21 1984-05-01 Handbury James W Aircraft recovery chute
GB2127764A (en) * 1982-09-30 1984-04-18 Jones Andrew Wil Free flyable structure
EP0130925A1 (de) * 1983-03-11 1985-01-09 Stephen L. Snyder Motorisierter Hängeleiter mit fallschirmförmigem Tragflügel
DE3321499A1 (de) * 1983-06-15 1984-01-05 Dieter Dipl.-Ing. Unbehaun (FH), 8500 Nürnberg Eigenstartfaehiges luftfahrzeug mit geringen packmassen

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108945427A (zh) * 2018-07-24 2018-12-07 深圳市百川融创科技有限公司 用于冲压翼伞的弹射回收装置
CN108945427B (zh) * 2018-07-24 2023-12-29 深圳市百川融创科技有限公司 用于冲压翼伞的弹射回收装置
CN109823531A (zh) * 2019-03-13 2019-05-31 深圳市百川融创科技有限公司 一种基于冲压翼伞绳的弹射回收装置
CN109823531B (zh) * 2019-03-13 2023-12-29 深圳市百川融创科技有限公司 一种基于冲压翼伞绳的弹射回收装置

Also Published As

Publication number Publication date
EP0217686B1 (de) 1988-10-19
FR2585668B1 (fr) 1987-11-20
DE3660954D1 (en) 1988-11-24
FR2585668A1 (fr) 1987-02-06

Similar Documents

Publication Publication Date Title
EP0392911A1 (de) Einrichtung, um ein Motorrad in ein motorisiertes Ultraleichtflugzeug zu verwandeln
FR2679199A1 (fr) Systeme anticouple pour helicoptere.
US20180215434A1 (en) Central wheel structure auto-balancing device
FR2623318A1 (fr) Manege a effet ascensionnel equipe d'un avion
EP0217686B1 (de) Flugzeug des Fallschirmflügeltyps
WO2007056294A2 (en) A method and means for piloting control of a forward-moving vehicle
EP0160597B1 (de) Flugmanövrierbare Fallschirmkappe und Steuerungsverfahren für die Fallschirmkappe
US4824047A (en) Hang glider launch vehicle
FR2761332A1 (fr) Dispositif de reduction des transferts de charge des vehicules a 2 roues tels que motocyclettes et velomoteurs
FR2624828A1 (fr) Harnais sellette pour parachute du type a aile souple
FR2630704A1 (fr) Fuselage motorise agence pour etre suspendu a une voilure
WO1986004836A1 (fr) Avion convertible
FR2943622A3 (fr) Appareil ultraleger motorise
EP0317554B1 (de) Servosteuerungsvorrichtung eines drehflügelflugzeuges
WO1986007329A1 (fr) Appareil volant ultra-leger motorise a helice rabattable
EP2418146A1 (de) Leichtes Luftfahrzeug mit Motorantrieb und verbessertem Gleichgewichtsausgleich
FR3000666A1 (fr) Vehicule pour l'embarquement et le transport d'une personne sur fauteuil roulant
EP0971840A1 (de) Vorrichtung zum betrieb eines seitenruders eines flugzeuges und flugzeug ausgerustet mit dieser vorrichtung
EP0575344B1 (de) Fliegendes fahrzeug, wie motorisiertes ultraleichtes flugzeug
KR100242158B1 (ko) 경비행기
FR2657060A1 (fr) Vehicule routier a faible resistance a la penetration dans l'air, et prenant appui sur l'air pour ameliorer sa tenue de route.
FR2543512A1 (fr) Dispositif de propulsion notamment pour aeronefs du genre aile libre, ainsi que les aeronefs equipes de ce dispositif
FR2618123A1 (fr) Hydravion ultra-leger
FR2552395A1 (fr) Perfectionnements apportes aux helices sustentatrices pour aeronefs
FR2650553A1 (fr) Aeronef type pendulaire a pilotage trois axes a voilure a surface variable dont le deploiement, le repliage et le reglage sont commandes

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): BE DE GB IT

17P Request for examination filed

Effective date: 19870611

17Q First examination report despatched

Effective date: 19880310

ITF It: translation for a ep patent filed

Owner name: DE DOMINICIS & MAYER S.R.L.

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: AERONAUTIQUE SERVICE

RIN1 Information on inventor provided before grant (corrected)

Inventor name: RANJON, MARC

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): BE DE GB IT

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)
REF Corresponds to:

Ref document number: 3660954

Country of ref document: DE

Date of ref document: 19881124

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 19900730

Year of fee payment: 5

Ref country code: BE

Payment date: 19900730

Year of fee payment: 5

ITTA It: last paid annual fee
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 19900926

Year of fee payment: 5

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Effective date: 19910729

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Effective date: 19910731

BERE Be: lapsed

Owner name: AERONAUTIQUE SERVICE

Effective date: 19910731

GBPC Gb: european patent ceased through non-payment of renewal fee
PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Effective date: 19920401

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.

Effective date: 20050729